User:Govindarasu Shivaji/sandbox

SOLID PROPELLANTS IN ROCKETS. ABSTRACT In this article, we are increasing the fuel storage efficiency in the rockets. This is useful in rocket science for travelling more distance with more fuel. The normal weight of the fuel in the liquid storage is much higher than the solid storage. We are converting the liquid form of fuel to solid form by decreasing the temperature. The weight of the fuel will decrease by converting the liquid to solid we can get more space in fuel chambers and we can add some extra fuel in fuel chambers, (for extra space=liquid fuel weight-solid fuel weight). This technique will help us to travel more distance by rocket. This technique is most useful for astronauts for store oxygen on space much more than normal.

1. INTRODUCTION: The modern solid propellants are composed of black powder with the ingredients (sulphur, charcoal, and saltpetre) these are used from the 13th century in Asia. After a big hard work, these applications are introduced in military applications. After successfully introduced in the military applications. In 1945 successfully started in the space activities. In the year of (1232) the Chinese writer and philosopher, “Jiao yu” is used the solid propellant rockets it is “fire arrows” after a long time so many inventors are trying to implement the solid propellants in rockets. In that, [1] Chapters 1–2, Blazing the trail: the early history of spacecraft and rocketry, Mike Grunt man, [2] Hu, Wen-Rue (1997). Space Science in China (published August 20, 1997). p. 15, [3] M. D. Black (2012). The Evolution of Rocket Technology. Native Planter, SLC. p. 39, [4] Minotaur IV User's Guide, Release 1.0, Orbital Science Corp., January 2005, p. 4, [5] Sawka, Wayne N.; McPherson, Michael (12 July 2013). "Electrical Solid Propellants: A Safe, Micro to Macro Propulsion Technology". • Nowadays, for a fuel vehicle, we need fuel efficiency but we are not giving much preference for the capacity of fuel storage containers. But in the space-travelling vehicles like the space shuttle, rockets. But in space travel, the important thing we need to consider that the fuel storage and the fuel efficiency on the rockets. The exclusive reports by NASA (National Aeronautics and space administration) is, • The external tank held 535,000 gallons (2,024,975Liters) of propellants. • A part of the external tank which is filled with 390,000 gallons (1,476,150Liters) of liquid hydrogen. • Another part of the external tank is filled with 145,000 gallons (548,825Liters) of liquid oxygen. • Which space shuttle main engines through 17-inches of diameter feedlines. • Let's discuss the conversion of liquid which is present in the estimated volume by using the below formula. • We know that; L=3.142*(R*R) *H*1000 Where: • R= the radius of the fuel tank (units: -meter), • H= the height of the fuel tank (meter), L = the amount of fuel stored in the fuel tank (units: -litres). Let we assume that a fuel tank which radius 1 meter and the height of the tank is 1meter; Now applying the formula, we have that, R=1m, H=1m; V=3.142*(R*R) *(H)*1000 V=3.142*(1*1) *1*1000 V=3.142*1000 V=3142.18 l Consider another example consider the radius of the tank is 5 meters and the height of the tank is 9 meters; Given: R=5m, H=9m; V=3.142*(R*R) *(H)*1000 V=3.142*(5*5) *(9) *1000 V=3.142*25*9*1000 V=706,950 l.

1.1 ROCKET SCIENCE: • Basically, in rockets the fuel is in the form of a liquid but, here we go, we will get the more space in the fuel tank for adding more liquid oxygen by converting liquid state of the oxygen to solid state of the oxygen. i.e. (-183degree Celsius to -218degree Celsius). Normally, -183degree Celsius is used in rockets for cooling liquid oxygen in storage tanks. In rockets, liquid hydrogen is maintaining with the temperature of -252.87degree Celsius to make solid hydrogen we need to decrease the temperature to -259.14degree Celsius in the hydrogen storage tanks. • Let we consider that the three layers are containing in the rocket fuel tanks and storage containers. The first inner layer of the fuel tank is made with two loop layers of rubber and the second layer of the tank is made with the dielectric material to maintaining the temperature of the fuel which is located inside. In between these two layers, we are having that thermoforming machine to increase the temperature this process can melt the fuel inside the tank. We are having another one layer which is made up of weightless metal like aluminium layer to protect from the external disturbances for the storage tanks.

2. DIELECTRICS: All dielectrics are insulators, here we are using dielectrics in fuel tanks to maintain the constant temperature. Normally, in conductors the thermal conductivity is high but, in dielectrics, thermal conductivity is varying with different stages. Consider "C-STOCK 265" is a dielectric in which weight is less than cotton. So we can use this dielectric in a rocket fuel tank. The "C-STOCK 265" is an artificial dielectric which is the thinnest dielectric. By forming the layer by layer it will get the properties of its own. By this property, it can maintain the temperature at constant. Fig.1 fuel tank design. • Here, we can see the three different layers from this rocket fuel model diagram.in this diagram. the innermost layer is the 1st Hoop layer and the next layer is the helical layer and to compress the tank we are introducing the same process to the tank by introducing the 2nd Hoop layer and stretch tapes over the 2nd loop. Use the principle of oven cure to make hard by heating the layers and unwrap the tapes. By this, we are making the large fuel tanks. • In this process, we are making the small addition with this process which is we are using the dielectrics to maintain the constant temperature to the fuel tank and we are introducing the heat generating system which is surrounding the tank. By this process, we can melt the frozen fuel by applying heat outside. After getting the liquid fuel the process will continue which is used in the liquid propellants. Liquid à kilogram > liquid à solid à kilogram 2H2+O2à2H2O+ENERGY Here, when the hydrogen and oxygen and react inside in the combustion chamber it will produce more energy of 7.5 million of thrust is produced in this chamber with the water stream. It is passed to the engine and it was making the more thrust to move upwards to the rockets.

3. PRINCIPLE IN SOLID PROPELLANTS: The normal weight of the one litre of oxygen = 1.141kilograms. The normal quantity of the one kilogram of hydrogen = 14.128litres. The Saturn V rocket's first stage carries the 203,400 gallons (770,000litres) of kerosene fuel and 318,000 gallons (1.2 million litres) of liquid oxygen needed for combustion at lift off the stage five F_1 rocket engines ignite. • No of litres of kerosene =770,000L=631,477kg. • No of litres of liquid oxygen =1,200,000L=1,051,200kg. • The solid weight of the kerosene is =619,080kg. • The solid weight of the oxygen is =775,920kg. The above calculations show that liquid fuel is greater than the solid weight of the fuel. Now we will see how to reduce the weight of the rocket by converting liquid to solid fuel. Propellants (fuels) are used in the rockets: - • Liquid oxygen(LOX) • Kerosene(RP-1) Liquid oxygen (LOX):- • The melting point and freezing point of oxygen are (-218.8 degree Celsius). • The boiling point of the oxygen is (-183 degree Celsius). Kerosene (RP-1): - • The melting point and freezing point of kerosene are (-47 degree Celsius). • The boiling point of the kerosene is (in between 37 and 65 degree Celsius). As we know, in rockets they are at different stages. • First stage, • Second stage, • Third stage, • Fourth stage. We take the rocket PSLV (polar satellite launching vehicle) in this, the amount of propellant used in different stages are given below • First stage:- 138,200 kg (both fuel and oxygen), • Second stage: - 42,000 kg (both fuel and oxygen), • Third stage - 7,600 kg (both fuel and oxygen), • Fourth stage: - 2,500 kg (both fuel and oxygen). Optimum mixture ratio: Here the Propellants contains both fuel and oxygen Therefore, we have to find the ratio of fuel and oxygen, In this mode, we will consider the ratio of oxygen and fuel are 3:2 respectively. • First stage: - 138,200 kg (both fuel and oxygen), Here according to the Propellants Optimum mixture ratio, the amount of fuel is 54,037 kg And the amount of oxygen is 84,163 kg. • Second stage: - 42,000 kg (both fuel and oxygen), Here according to the Propellants Optimum mixture ratio, the amount of fuel is 16,422 kg And the amount of oxygen is 25,578 kg. • Third stage: - 7,600 kg (both fuel and oxygen), Here according to the Propellants Optimum mixture ratio, the amount of fuel is 2,932.5 kg And the amount of oxygen is 4,567.5 kg. • Fourth stage: - 2,500 kg (both fuel and oxygen), Here according to the Propellants Optimum mixture ratio, the amount of fuel is 977.5 kg And the amount of oxygen is 1,522.5 kg. 1 gallon of liquid= 3.785 kg, 1 gallon of solid ice= 2.44 kg. The difference between liquid and solid ice=3.785-2.44=1.345kg. • First stage=138,200/1.345=102,750.929kg. • Second stage=42,000/1.345=31,226.765kg. • Third stage=7,600/1.345=5,650.557kg. • Fourth stage=2,500/1.345=1,858.736kg.

4. APPLICATIONS: • By installation of this mechanism, we can travel space longer than usual using rockets and space shuttle. • We can store oxygen in solid-state in space and underwater, we can use it a longer time than normal.

5. RESULT AND DISCUSSION: By using solid propellants, the rockets can travel more distance than normal.it is verified with the calculations Solid weight of fuel < liquid weight of fuel. Here, in fig.2, we are representing the propellants weigh in different stages in the rocket propellants. Observe that normally the weight of liquid is 87.71% greater than the weight of solid. Observe this graph carefully fig.3; you can say that the weight of propellants is differing from the different stages. So, by using the solid fuel instead of liquid fuel we can add more fuel in the fuel storage tank.

6. CONCLUSION: In summary, This technique is not only useful for propellants we can use this principle for some other machines. Fuel is more effective for the engines, but not only for the world is fuel also needed for humans to survive the world. By using the more fuel the environment is getting more and more damaging but at the same time, we need to think about the fuel consumption.

7. REFERENCES: [1] Chapters 1–2, Blazing the trail: the early history of spacecraft and rocketry, Mike Grunt man, AIAA, 2004, ISBN 1-56347-705-X [2] Hu, Wen-Rue (1997). Space Science in China (published August 20, 1997). p. 15. ISBN 978- 9056990237. [3] M. D. Black (2012). The Evolution of Rocket Technology. Native Planter, SLC. p. 39. Payloadz.com under eBook/History [4] Minotaur IV User's Guide, Release 1.0, Orbital Sciences Corp., January 2005, p. 4 [5] Sawka, Wayne N.; McPherson, Michael (12 July 2013). "Electrical Solid Propellants: A Safe, Micro to Macro Propulsion Technology". American Institute of Aeronautics and Astronautics. doi:10.2514/6.2013-4168.